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Self-throwing fairings and rockets

A fairing and rocket technology, applied in space navigation equipment, space navigation aircraft, space navigation equipment and other directions, to overcome the influence of resistance and high temperature environment, the separation speed is fast, and the output performance is stable and reliable.

Active Publication Date: 2022-07-15
湖北航天飞行器研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Because the rocket is flying at high speed in the atmosphere, the separation environment is very harsh. The traditional method of throwing the fairing away after the rocket breaks out of the atmosphere to release its internal spacecraft and the corresponding structure, because of this design The object of use is used under relatively small resistance after rushing out of the atmosphere, and the separation driving force provided by its separation structure can no longer meet the demand in the very harsh environment of high temperature and large wind resistance.

Method used

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  • Self-throwing fairings and rockets
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  • Self-throwing fairings and rockets

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] like figure 1 As shown, the self-throwable fairing 100 is connected to the head of the rocket body through the docking bracket 5, including:

[0051] The fairing shell includes at least two fairing pieces, and the fairing pieces are spliced ​​and connected at least through a radial connection mechanism.

[0052] The shroud-throwing separation system, which receives the control commands of the rocket body and performs actions, includes a separation output mechanism and an axial connection mechanism arranged in the fairing shell. The axial connecting mechanism is used to connect the docking bracket 5 and the fairing shell.

[0053] Wherein, the separation output mechanism is used to push the fairing shell to be separated according to a predetermined separation speed and attitude after the connection between the radial connection mechanism and the axial connection mechanism is released.

Embodiment 2

[0055] On the basis of Embodiment 1, as a specific preference, the radial connection mechanism is a radial connection and separation bolt 4, which is arranged in the middle of the fairing sheet, and is used to connect the assembled at least two fairing sheets. When the separation bolt receives the separation signal, it acts to release or weaken the connection; and / or

[0056] The axial connection mechanism is an axial connection and separation bolt 7, which is arranged at the tail of the fairing body and is used to axially connect and fix the fairing shell and the docking bracket, such as image 3 , 5 , 7, the axial connection separation bolt 7 is used to connect the docking bracket and the control cabin, and at the same time as shown in Figure 5 As shown in the figure, it can be seen that the docking bracket and the control cabin are auxiliaryly connected through the stud bolt S. When the separation bolt receives the separation signal from the control cabin, it is activated...

Embodiment 3

[0060] In the basic line of Embodiment 1-2, as a specific preference, the separation output mechanism includes a front-end separation output actuator 3 arranged in the head of the fairing shell, and the two ends of the front-end separation output actuator are respectively connected with the phase The corresponding interface connection set on the adjacent fairing body, such as figure 2 , 3 As shown in the figure, when the front-end separation output actuator receives the separation signal, it will act to spread the corresponding fairing piece for separation; and / or

[0061] The separation output mechanism includes a rear end separation output actuator 6 arranged at the rear of the fairing shell, and the rear end separation output actuator has a body 61 and a push rod 62, such as Image 6 , 9 , 10, 11, 12, the body is a closed cavity, and the interior is equipped with a prefabricated powder block and a detonator (current detonator, such as an electric detonator), and the deto...

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Abstract

The self-throwable fairing is connected to the head of the rocket body through a docking bracket, and includes: a fairing shell, including at least two shunt shroud pieces, the shunt shroud pieces are at least spliced ​​and connected by a radial connection mechanism; The cover separation system, which receives the control commands of the rocket body and performs actions, includes a separation output mechanism and an axial connection mechanism arranged in the fairing shell. The axial connection mechanism is used to connect the docking bracket and the fairing shell, wherein the separation output mechanism It is used to push the fairing shell to separate according to a predetermined separation speed and attitude after the connection between the radial connection mechanism and the axial connection mechanism is released. Because a throwing separation system is set in the fairing shell, work is done by the active action of the separation output mechanism of the throwing separation system, which overcomes the resistance in the hypersonic state and the influence of the high temperature environment, the separation speed is fast, and the output performance is stable and reliable. , which can be used for fairing separation in harsh environmental conditions.

Description

technical field [0001] The invention relates to a fairing and a rocket, in particular to a self-throwing fairing and a rocket, belonging to the field of rocket structures. Background technique [0002] The fairing of the rocket plays the role of reducing the air resistance of the rocket and protecting the spacecraft inside. With the development of science and technology and the growing rise of the basic scientific research on the aerodynamic characteristics of hypersonic speed in China, new requirements are also put forward for the launch vehicle. Without leaving the atmosphere, the rocket flung the fairing away at hypersonic speeds, releasing its interior spacecraft. [0003] Since the rocket is flying at high speed in the atmosphere, the environment for throwing the hood is very harsh. Traditionally, when the rocket rushes out of the atmosphere, the fairing is thrown away to release the inner spacecraft and the corresponding structure. Because of this design The object of...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 薛士明索桂兰李盛徐禄高海军巩立先
Owner 湖北航天飞行器研究所